In aviation, sustaining certain attitudes during flight such as level, straight and high flying, ascents, and descents requires exact control of the pitch angles of the aircraft. The non-linear and unpredictable dynamics of aircraft cause difficulties for traditional control systems. To address these challenges, we propose a filtered PID (PID-F) controller for airplane pitch-angle control, with parameters tuned using the geometric mean optimizer (GMO). By including a filter parameter to the derivative gain, this combination attempts to efficiently reduce the kick effect and improve the stability and performance of the aircraft pitch control system. The optimization approach is guided by a time-domain-based objective function utilized in the study. The suggested GMO/PID-F approach's consistency and stability are confirmed by the simulation results. The effectiveness of the recommended approach is demonstrated by a comparison analysis of many optimization techniques used in controllers from the literature. In particular, the GMO/PID-F controller demonstrates precision control, no overshoot, quick rise time, and short settling time. The results show that the suggested technique is an effective way to optimize aircraft pitch angle control systems, providing increased reliability as well as effectiveness.